Stator segment circumferential gap seal

Abstract

A vane assembly for a gas turbine includes a first shroud segment, a second shroud segment, a first inner air seal, and a seal assembly. The first shroud segment has a first end face. The second shroud segment is disposed adjacent to the first shroud segment and has a second end face that faces towards and is spaced apart from the first end face by a gap. The first inner air seal extends into the first shroud segment and defines a first trench. The seal assembly at least partially received within the first trench.

What is claimed is: 
     
       1. A vane assembly for a gas turbine engine, comprising:
 a first shroud segment having a first end face; 
 a second shroud segment disposed adjacent to the first shroud segment and having a second end face that faces towards and is spaced apart from the first end face by a gap; 
 a first inner air seal that extends into the first shroud segment and defines a first trench; 
 a second inner air seal disposed adjacent to the second shroud segment and being arranged for engagement with the second shroud segment; and 
 a seal assembly including a hollow member made of a first material and a fill disposed within the hollow member that is made of a second material, the seal assembly at least partially received within the first trench and engaged to an inner surface of the first shroud segment and an inner surface of the first inner air seal. 
 
     
     
       2. The vane assembly of  claim 1 , wherein the seal assembly is at least partially received between the second inner air seal and the second shroud segment. 
     
     
       3. The vane assembly of  claim 2 , wherein the seal assembly engages an inner surface of the second inner air seal. 
     
     
       4. A vane assembly for a gas turbine engine, comprising:
 a first shroud segment having a first platform, a first leg extending from the first platform, and a second leg extending from the first platform and spaced apart from the first leg; 
 a first inner air seal at least partially extends into the first shroud segment, the first inner air seal having a first face, a second face spaced apart from the first face, a first surface that engages the first leg, a second surface that engages the second leg, a third surface disposed parallel to the first surface and the second surface and spaced apart from the first platform, a fourth surface extending between the first surface and the third surface, and a fifth surface extending between the second surface and the third surface, the first inner air seal defining a first trench therebetween; and 
 a seal assembly including a hollow member that is spaced apart from the first platform, the first leg, and the second leg, the seal assembly further including a pedestal that is operatively connected to the hollow member, and the seal assembly being received within the first trench. 
 
     
     
       5. The vane assembly of  claim 4 , wherein the pedestal engages the second face and engages at least one of the first surface, the second surface, the third surface, the fourth surface, and the fifth surface. 
     
     
       6. The vane assembly of  claim 5 , wherein the pedestal engages the first leg, the second leg, and the first platform. 
     
     
       7. A gas turbine engine, comprising:
 a vane assembly provided with at least one of a fan section and a compressor section, the vane assembly comprising:
 a first shroud segment disposed adjacent to and spaced apart from a second shroud segment, the first shroud segment having a first leg and a second leg each extending from a first platform, 
 a first inner air seal disposed adjacent to and spaced apart from a second inner air seal, the first inner air seal extends into the first shroud segment and defines a first trench between a first face and a second face of the first inner air seal, and 
 a seal assembly including a hollow member extending between a first end that engages a first surface of the first inner air seal that extends between the first face and the second face and a second end that engages a second surface of the first inner air seal that is spaced apart from the first surface and extends between the first face and the second face, the hollow member having a first portion extending from the first end and being spaced apart from the first leg, a second portion extending from the second end and being spaced apart from the second leg, and a third portion extending between the first portion and the second portion and being spaced apart from the first platform, 
 the seal assembly including a pedestal that is operatively connected to the hollow member and engages the second face, the seal assembly beings at least partially disposed within the first trench. 
 
 
     
     
       8. The gas turbine engine of  claim 7 , wherein the hollow member has a first portion extending from the first end and engages the first leg, a second portion extending from the second end and engages the second leg, and a third portion extending between the first portion and the second portion and engages the first platform. 
     
     
       9. The gas turbine engine of  claim 7 , wherein a fill is disposed within the hollow member.